CN215622661U - Undercarriage and fixed wing unmanned aerial vehicle - Google Patents
Undercarriage and fixed wing unmanned aerial vehicle Download PDFInfo
- Publication number
- CN215622661U CN215622661U CN202121268172.9U CN202121268172U CN215622661U CN 215622661 U CN215622661 U CN 215622661U CN 202121268172 U CN202121268172 U CN 202121268172U CN 215622661 U CN215622661 U CN 215622661U
- Authority
- CN
- China
- Prior art keywords
- unmanned aerial
- aerial vehicle
- undercarriage
- rod
- connecting rod
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Landscapes
- Forklifts And Lifting Vehicles (AREA)
Abstract
The utility model discloses an undercarriage and a fixed wing unmanned aerial vehicle, wherein the undercarriage is detachably arranged on the unmanned aerial vehicle to assist the unmanned aerial vehicle in landing, the undercarriage comprises a first landing frame, a second landing frame and a connecting mechanism for connecting the first landing frame and the second landing frame, the connecting mechanism comprises a first connecting rod and a second connecting rod which are mutually sleeved, and a first locking mechanism arranged between the first connecting rod and the second connecting rod, the first connecting rod and the second connecting rod can be relatively close to or far away from each other, and the relative position between the first connecting rod and the second connecting rod is locked through the first locking mechanism. Its manufacturing cost that can reduce fixed wing unmanned aerial vehicle and through the relative position of adjusting connecting mechanism in head rod and the second connecting rod, can make the undercarriage adapt to the fixed wing unmanned aerial vehicle of different wing widths to realize that an undercarriage satisfies a plurality of fixed wing unmanned aerial vehicle's effect.
Description
Technical Field
The utility model relates to the technical field of unmanned aerial vehicles, in particular to an undercarriage and a fixed wing unmanned aerial vehicle.
Background
With the development of science and technology, unmanned aerial vehicles become more and more popular. The fixed-wing unmanned aerial vehicle is an unmanned aerial vehicle with fixed wings, and the sweepback angle of the outer ends of the wings can be automatically or manually adjusted along with the speed. Due to excellent functions and modularized integration, the material is widely applied to the professions of surveying and mapping, geology, petroleum, agriculture and forestry and the like, and has wide market application prospect. The take-off and landing modes of the fixed-wing unmanned aerial vehicle are divided into two modes, one mode is gliding take-off and landing, and the other mode can be vertical take-off and landing.
This kind of fixed wing unmanned aerial vehicle that slides and take off and land can not be furnished with the undercarriage and descend, and this kind of fixed wing unmanned aerial vehicle is when descending, and the fixed wing unmanned aerial vehicle arrives the landing site overhead under the unchangeable condition of operation height to reduce flying height with the mode of circling, then replace the undercarriage device with the mode that the gentle belly landed and descend. Although this landing approach can reduce the cost and weight of the fixed wing drone, it can increase the loss of material from the belly of the fixed wing drone body. And most digital camera lens directly expose in the ventral position, when fixed wing unmanned aerial vehicle descends, because of the GPS precision is not enough to cause the skew flying spot when fixed wing unmanned aerial vehicle descends, very easily causes camera lens and ground foreign matter contact and damages.
When the fixed wing unmanned aerial vehicle that takes off and land perpendicularly is not furnished with the undercarriage, a landing mode is automatic parachuting, promptly at the landing in-process, when fixed wing unmanned aerial vehicle reachd predetermined recovery area central point overhead, the parachute that its was equipped with can be according to predetermined procedure or parachute-opening under the command of ground station, make fixed wing unmanned aerial vehicle slowly land, but the parachute is a load to fixed wing unmanned aerial vehicle, and need occupy limited space in the fuselage, because fixed wing unmanned aerial vehicle descending speed is very fast, in the landing moment, the organism receives stronger impact easily, cause the damage, it is great that free parachuting mode receives the influence of wind speed wind direction simultaneously.
There are also fixed wing drones equipped with landing gear for vertical take-off and landing on the market today, but this kind of landing gear of being equipped with is fixed directly at the fixed wing drone's organism belly. When the wing widths of the fixed wing drones are different, special undercarriage needs to be equipped for each type of fixed wing drone, which leads to the manufacturing cost of the fixed wing drone being too high, and when multiple types of fixed wing drones need to be used outdoors, multiple undercarriages need to be carried.
SUMMERY OF THE UTILITY MODEL
The utility model aims to provide an undercarriage and a fixed wing unmanned aerial vehicle, which can reduce the manufacturing cost of the fixed wing unmanned aerial vehicle, and can enable the undercarriage to adapt to fixed wing unmanned aerial vehicles with different wing widths by adjusting the relative positions of a first connecting rod and a second connecting rod in a connecting mechanism, so that one undercarriage can meet the effect of a plurality of fixed wing unmanned aerial vehicles.
The embodiment of the utility model is realized by the following steps:
in one aspect of the utility model, the undercarriage is detachably arranged on an unmanned aerial vehicle to assist the unmanned aerial vehicle in landing, and comprises a first landing gear, a second landing gear and a connecting mechanism for connecting the first landing gear and the second landing gear, wherein the connecting mechanism comprises a first connecting rod and a second connecting rod which are sleeved with each other, and a first locking mechanism arranged between the first connecting rod and the second connecting rod, the first connecting rod and the second connecting rod can be relatively close to or far away from each other, and the relative position between the first connecting rod and the second connecting rod is locked through the first locking mechanism.
Optionally, in an optional embodiment of the present invention, each of the first landing gear and the second landing gear includes a lifting mechanism, a supporting mechanism, a landing mechanism, and a fixing band, where the supporting mechanism connects the lifting mechanism and the landing mechanism, and the fixing band is disposed on the lifting mechanism and used for fixing with the drone.
Optionally, in an optional embodiment of the present invention, the fixing band includes a first fixing band and a second fixing band, the first fixing band is disposed on a side of the lifting mechanism that lifts the unmanned aerial vehicle, and the second fixing band is disposed on a side of the lifting mechanism that is away from the unmanned aerial vehicle.
Optionally, in an alternative embodiment of the present invention, the fixing strap includes a strap body and an adjusting mechanism disposed on the strap body, and the adjusting mechanism is configured to adjust a length of the fixing strap.
Optionally, in an optional embodiment of the present invention, the supporting mechanism includes a fixing rod and an adjusting rod that are sleeved with each other, and a second locking mechanism disposed between the fixing rod and the adjusting rod, the adjusting rod and the fixing rod may be relatively close to or far from each other, and a relative position between the adjusting rod and the fixing rod is locked by the second locking mechanism, and the fixing rod is connected to the lifting mechanism.
Optionally, in an optional embodiment of the present invention, the support mechanism further includes a buffer rod, the buffer rod is sleeved with the adjusting rod, and the buffer rod and the fixing rod are respectively located at two opposite sides of the adjusting rod.
Optionally, in an optional embodiment of the present invention, the internal accommodating space of the lifting mechanism is the same as the shape of the abdomen of the unmanned aerial vehicle.
Optionally, in an alternative embodiment of the present invention, the landing mechanism includes a landing lever disposed at an end of the adjusting lever away from a connection end of the adjusting lever and the fixed lever.
Optionally, in an alternative embodiment of the present invention, the material of the lifting mechanism, the material of the supporting mechanism, and the material of the landing mechanism are all carbon fibers.
In another aspect of the utility model, a fixed wing drone is provided, which includes a fixed wing drone body and any one of the above landing gears, wherein the landing gear is detachably arranged on the belly of the fixed wing drone body.
The beneficial effects of the utility model include:
the utility model provides an undercarriage and a fixed wing unmanned aerial vehicle. The undercarriage includes first landing gear, second undercarriage and connects the coupling mechanism of first landing gear and second undercarriage together, and coupling mechanism is including the head rod and the second connecting rod that cup joint each other to and set up the first locking mechanism between head rod and second connecting rod, and head rod and second connecting rod can be close to relatively or keep away from, and lock the relative position between head rod and the second connecting rod through a locking mechanism. The undercarriage can be dismantled and set up on unmanned aerial vehicle to need not be equipped with the undercarriage for each unmanned aerial vehicle, with reduction unmanned aerial vehicle manufacturing cost. Through the relative position of adjustment head rod and second connecting rod, can adjust the relative position of first landing gear and second undercarriage on unmanned aerial vehicle together, can make the unmanned aerial vehicle of undercarriage adaptation different wing width to realize that an undercarriage satisfies a plurality of unmanned aerial vehicle's effect.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.
FIG. 1 is a schematic illustration of a landing gear configuration provided by an embodiment of the present invention;
fig. 2 is a schematic structural diagram of a fixed-wing drone provided in an embodiment of the present invention.
Icon: 100-first landing; 110-a lifting mechanism; 120-fixing the belt; 121-an adjusting mechanism; 122-a first securing strap; 123-a second securing strap; 130-a support mechanism; 131-a fixing rod; 132-a second locking mechanism; 133-adjusting rod; 140-a landing mechanism; 200-a second landing gear; 300-a connection mechanism; 310-a first connecting rod; 320-a first locking mechanism; 330-a second connecting rod; 1000-undercarriage; 2000-fixed wing drone body.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the present invention, presented in the figures, is not intended to limit the scope of the utility model, as claimed, but is merely representative of selected embodiments of the utility model. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings or orientations or positional relationships that the products of the present invention are conventionally placed in use, and are only for convenience of describing the present invention and simplifying the description, but do not indicate or imply that the device or element to which the description refers must have a specific orientation, be constructed in a specific orientation, and be operated, and thus should not be construed as limiting the present invention. Furthermore, the terms "first," "second," "third," and the like are used solely to distinguish one from another and are not to be construed as indicating or implying relative importance.
Furthermore, the terms "horizontal", "vertical" and the like do not imply that the components are required to be absolutely horizontal or pendant, but rather may be slightly inclined. For example, "horizontal" merely means that the direction is more horizontal than "vertical" and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.
In the description of the present invention, it should also be noted that, unless otherwise explicitly specified or limited, the terms "disposed," "mounted," "connected," and "connected" are to be construed broadly and may, for example, be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
The embodiment of the utility model provides an undercarriage 1000, and the undercarriage 1000 is detachably arranged on the belly of an unmanned aerial vehicle body. It can reduce fixed wing unmanned aerial vehicle's manufacturing cost and through the relative position of adjusting connecting mechanism 300 in head rod 310 and second connecting rod 330, can make undercarriage 1000 adapt to the unmanned aerial vehicle of different wing widths to realize that an undercarriage 1000 satisfies a plurality of unmanned aerial vehicle's effect. A first embodiment of the present application will be described below with reference to the accompanying drawings.
First embodiment
Referring to fig. 1, the present embodiment provides a landing gear 1000, which includes a first landing gear 100, a second landing gear 200, and a connecting mechanism 300 for connecting the first landing gear 100 and the second landing gear 200, wherein the connecting mechanism 300 includes a first connecting rod 310 and a second connecting rod 330 that are sleeved with each other, and a first locking mechanism 320 disposed between the first connecting rod 310 and the second connecting rod 330, and the first connecting rod 310 and the second connecting rod 330 can be relatively close to or far from each other, and the first locking mechanism 320 locks the relative position between the first connecting rod 310 and the second connecting rod 330.
Wherein, this undercarriage 1000 can be dismantled and set up on unmanned aerial vehicle to need not be equipped with undercarriage 1000 for each unmanned aerial vehicle, thereby reduce unmanned aerial vehicle manufacturing cost. Through the relative position of adjustment head rod 310 and second connecting rod 330, can adjust the relative position of first undercarriage 100 and second undercarriage 200 on unmanned aerial vehicle together, can make undercarriage 1000 adapt to the unmanned aerial vehicle of different wing widths to realize that an undercarriage 1000 satisfies a plurality of unmanned aerial vehicle's effect.
It should be noted that, the present application does not limit the specific structure of the first locking mechanism 320, as long as the first locking mechanism 320 can lock the relative position of the first connecting rod 310 and the second connecting rod 330 after adjusting the relative position of the first connecting rod 310 and the second connecting rod 330. Illustratively, in the embodiment of the present invention, the first locking mechanism 320 includes 8 circular holes uniformly arranged on the first connecting rod 310 and a protrusion capable of extending and retracting up and down arranged on the second connecting rod 330, when adjusting the relative position of the first connecting rod 310 and the second connecting rod 330, the protrusion on the second connecting rod 330 is pressed into the rod body of the second connecting rod 330, then the relative position of the second connecting rod 330 and the first connecting rod 310 is adjusted, and after the adjustment, the protrusion bounces and passes through the circular hole on the first connecting rod 310 to lock the relative position of the first connecting rod 310 and the second connecting rod 330.
The first landing gear 100 and the second landing gear 200 may only lift the unmanned aerial vehicle and assist the unmanned aerial vehicle to land and land, and this example provides a specific form of the first landing gear 100 and the second landing gear 200, please refer to fig. 1, as shown in fig. 1, the first landing gear 100 and the second landing gear 200 each include a lifting mechanism 110, a supporting mechanism 130, a landing mechanism 140, and a fixing band 120, the supporting mechanism 130 connects the lifting mechanism 110 and the landing mechanism 140, and the fixing band 120 is disposed on the lifting mechanism 110 and used for fixing with the unmanned aerial vehicle.
The supporting mechanism 130 includes two ends, one end of which is connected to the lifting mechanism 110, and the other end of which is connected to the landing mechanism 140.
It should be noted that the fixing band 120 and the lifting mechanism 110 may be fixed as long as the landing gear 1000 and the drone are detachably fixed. Exemplarily, one end of the fixing band 120 is fixedly connected to the lifting mechanism 110, wherein the fixing band 120 is connected to the lifting mechanism 110 by a bolt, or one end of the fixing band 120 is bonded to the lifting mechanism 110, the other end of the fixing band 120 is detachably connected to the lifting mechanism 110, wherein the other end of the fixing band 120 is connected to the clamping member by a detachable manner, the clamping member is disposed at the other end of the fixing band 120, the clamping groove is disposed on the lifting mechanism 110, the clamping member is pressed into the clamping groove during installation, the other end of the fixing band 120 is connected to the lifting mechanism 110, the clamping member is taken out of the clamping groove during detachment, so as to detach the undercarriage 1000 from the unmanned aerial vehicle, or the magic tape mechanism is used, the other end of the fixing end is bonded to the lifting mechanism 110 during fixing, and the other end of the fixing end is removed from the lifting mechanism 110 during detachment.
Optionally, as shown in fig. 1, in an embodiment of the present invention, the fixing strap 120 includes a first fixing strap 122 and a second fixing strap 123, the first fixing strap 122 is disposed on a side of the lifting mechanism 110 that lifts the unmanned aerial vehicle, and the second fixing strap 123 is disposed on a side of the lifting mechanism 110 that is away from the unmanned aerial vehicle. Wherein, only need to set up in lifting mechanism 110 and lift first fixed band 122 of unmanned aerial vehicle one side and untie and can install when fixing undercarriage 1000 to unmanned aerial vehicle.
Alternatively, as shown in fig. 1, in the embodiment of the present invention, the fixing strap 120 includes a strap body and an adjusting mechanism 121 disposed on the strap body, and the adjusting mechanism 121 is used for adjusting the length of the fixing strap 120. The tightness degree of the fixing belt 120 for fixing the unmanned aerial vehicle and the landing gear 1000 can be adjusted by adjusting the length of the fixing belt 120.
It should be noted that the adjusting mechanism 121 only needs to be able to adjust the length of the fixing strap 120, and the adjusting mechanism 121 may be a rotary buckle, and the length of the fixing strap 120 is adjusted by rotating a knob of the rotary buckle.
In practical applications, heights of the landing mechanism 140 and the lifting mechanism 110 need to be adjusted, and optionally, as shown in fig. 1, the supporting mechanism 130 includes a fixed rod 131 and an adjusting rod 133 that are sleeved with each other, and a second locking mechanism 132 that is disposed between the fixed rod 131 and the adjusting rod 133, the adjusting rod 133 and the fixed rod 131 can be relatively close to or far from each other, and a relative position between the adjusting rod 133 and the fixed rod 131 is locked by the second locking mechanism 132, and the fixed rod 131 is connected to the lifting mechanism 110.
It should be noted that the specific structure of the locking mechanism is not limited in the present application, as long as the locking mechanism can lock the relative position of the adjusting lever 133 and the fixing lever 131 after the relative position of the adjusting lever 133 and the fixing lever 131 is adjusted. For example, in the embodiment of the present invention, the second locking mechanism 132 may be the same as or different from the first locking mechanism, for example, the second locking mechanism 132 is a bolt disposed on the fixing rod 131 and passing through the cylindrical surface of the fixing rod 131, and after the relative position between the adjusting rod 133 and the fixing rod 131 is adjusted, the bolt is tightened, and the end of the bolt abuts against the cylindrical surface of the adjusting rod 133 to lock the relative position between the adjusting rod 133 and the fixing rod 131.
Optionally, in order to make unmanned aerial vehicle can steadily fall to the ground, reduce the vibration to the camera that unmanned aerial vehicle carried on and other original papers, supporting mechanism 130 still includes the buffer beam, and the buffer beam cup joints each other with adjusting pole 133, and the buffer beam is located the relative both sides of adjusting pole 133 respectively with dead lever 131. Wherein, the buffer rod can be a hydraulic support rod.
Optionally, referring to fig. 1, in an alternative embodiment of the present invention, the internal accommodating space of the lifting mechanism 110 is the same as the shape of the abdomen of the unmanned aerial vehicle. For example, in the present embodiment, the belly of the drone is streamlined, so the inner accommodating space of the lifting mechanism 110 is also streamlined.
Optionally, referring to fig. 1, in an alternative embodiment of the present invention, the landing mechanism 140 includes a landing bar disposed at an end of the adjusting bar 133, which is far away from the end where the adjusting bar 133 is connected to the fixing bar 131. Where the axis of the landing lever is perpendicular to the axis of the adjustment lever 133.
Optionally, in order to reduce the load of the drone, the material of the lifting mechanism 110, the supporting mechanism 130 and the landing mechanism 140 is carbon fiber in this example. Carbon fiber material is guaranteeing that undercarriage 1000 has reliable strength and keeps very light weight to can increase unmanned aerial vehicle's time of endurance.
The utility model provides a landing gear 1000 device which is detachably arranged on an unmanned aerial vehicle to assist the landing of the unmanned aerial vehicle, and comprises a first landing gear 100, a second landing gear 200 and a connecting mechanism 300 for connecting the first landing gear 100 and the second landing gear 200, wherein the connecting mechanism 300 comprises a first connecting rod 310 and a second connecting rod 330 which are sleeved with each other, and a first locking mechanism 320 arranged between the first connecting rod 310 and the second connecting rod 330, the first connecting rod 310 and the second connecting rod 330 can be relatively close to or far away from each other, and the relative position between the first connecting rod 310 and the second connecting rod 330 is locked through the first locking mechanism 320. Undercarriage 1000 can be dismantled and set up on unmanned aerial vehicle to need not be equipped with undercarriage 1000 for each unmanned aerial vehicle, can reduce unmanned aerial vehicle manufacturing cost. Through the relative position of adjustment head rod 310 and second connecting rod 330, can adjust the relative position of first undercarriage 100 and second undercarriage 200 on unmanned aerial vehicle together, can make undercarriage 1000 adapt to the unmanned aerial vehicle of different wing widths to realize that an undercarriage 1000 satisfies a plurality of unmanned aerial vehicle's effect.
Second embodiment
In another aspect of the present invention, as shown in fig. 2, there is provided a fixed wing drone, which includes a fixed wing drone body 2000 and an undercarriage 1000, wherein the undercarriage 1000 is detachably disposed on an abdomen of the fixed wing drone body 2000.
It should be noted that in alternative embodiments of the present invention, fixed wing drones may be more specifically referred to as fixed wing drones that land vertically, given that those drones that land in a taxiing mode may not use the landing gear 1000 during landing.
The fixed wing unmanned aerial vehicle provided by the utility model has lower manufacturing cost, and when the landing gear 1000 is not needed and the relative positions of the first connecting rod 310 and the second connecting rod 330 in the connecting mechanism 300 are adjusted, the landing gear 1000 can adapt to fixed wing unmanned aerial vehicles with different wing widths, so that the effect that one landing gear 1000 meets a plurality of fixed wing unmanned aerial vehicles is realized.
The above description is only an alternative embodiment of the present invention, and is not intended to limit the present invention, and various modifications and variations of the present invention may occur to those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
It should be noted that the various technical features described in the above embodiments can be combined in any suitable manner without contradiction, and the utility model is not described in any way for the possible combinations in order to avoid unnecessary repetition.
Claims (10)
1. The utility model provides an undercarriage, can dismantle to set up in unmanned aerial vehicle in order to assist unmanned aerial vehicle lands, a serial communication port, the undercarriage includes first landing gear, second undercarriage and connects together the first landing gear with the coupling mechanism of second undercarriage, coupling mechanism is including the head rod and the second connecting rod that cup joint each other, and sets up the head rod with first locking mechanism between the second connecting rod, the head rod with the second connecting rod can be close to relatively or keep away from, and pass through first locking mechanism locks the head rod with relative position between the second connecting rod.
2. A landing gear according to claim 1, wherein the first landing gear and the second landing gear each include a lifting mechanism, a support mechanism, a landing mechanism and a securing strap, the support mechanism connecting the lifting mechanism and the landing mechanism, the securing strap being provided on the lifting mechanism for securing with the drone.
3. A landing gear according to claim 2, wherein the fixing strap comprises a first fixing strap and a second fixing strap, the first fixing strap being disposed on a side of the lifting mechanism that lifts the unmanned aerial vehicle, and the second fixing strap being disposed on a side of the lifting mechanism that is remote from the unmanned aerial vehicle.
4. A landing gear according to claim 2, wherein the strap includes a strap and an adjustment mechanism provided on the strap for adjusting the length of the strap.
5. The landing gear according to claim 2, wherein the support mechanism includes a fixed rod and an adjusting rod sleeved with each other, and a second locking mechanism disposed between the fixed rod and the adjusting rod, the adjusting rod and the fixed rod can be relatively close to or far from each other, and the relative position between the adjusting rod and the fixed rod is locked by the second locking mechanism, and the fixed rod is connected to the lifting mechanism.
6. A landing gear according to claim 5, wherein the support mechanism further includes a bumper bar, the bumper bar being sleeved with the adjustment bar, the bumper bar and the fixed bar being located on opposite sides of the adjustment bar.
7. A landing gear according to claim 5, wherein the landing mechanism includes a landing lever disposed at an end of the adjustment lever remote from the end of the adjustment lever to which the fixed bar is connected.
8. A landing gear according to claim 2, wherein the internal volume of the lifting mechanism is the same shape as the belly of the drone body.
9. A landing gear according to claim 2, wherein the lifting mechanism, the support mechanism and the landing mechanism are all of carbon fibre.
10. A fixed wing unmanned aerial vehicle, characterized in that, including fixed wing unmanned aerial vehicle body and the undercarriage of any one of claims 1 ~ 9, the undercarriage detachable sets up in the organism belly of fixed wing unmanned aerial vehicle body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121268172.9U CN215622661U (en) | 2021-06-07 | 2021-06-07 | Undercarriage and fixed wing unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121268172.9U CN215622661U (en) | 2021-06-07 | 2021-06-07 | Undercarriage and fixed wing unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN215622661U true CN215622661U (en) | 2022-01-25 |
Family
ID=79941880
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202121268172.9U Active CN215622661U (en) | 2021-06-07 | 2021-06-07 | Undercarriage and fixed wing unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN215622661U (en) |
-
2021
- 2021-06-07 CN CN202121268172.9U patent/CN215622661U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US8308142B1 (en) | System and method for transporting cargo utilizing an air towing system that can achieve vertical take-off and vertical landing | |
| CN103347782B (en) | Aircraft | |
| EP3228537A1 (en) | Aircraft wing shift device | |
| CN107117285A (en) | Unmanned plane provided with foldable unmanned plane supporting member | |
| US20210354821A1 (en) | Flying Apparatus | |
| CN106394882B (en) | A kind of chute-type unmanned plane skid jack | |
| JP2019055766A (en) | Methods and apparatus for aligning and securing aircraft | |
| AU2020279955B2 (en) | Aircraft retrieval system and method | |
| CN207466961U (en) | The collapsible undercarriage and its foldable structure of balloon borne near space solar energy unmanned plane | |
| JP2022529504A (en) | Ground support equipment for high altitude long cruising time aircraft | |
| CN107512394A (en) | A kind of tail sitting posture VUAV and flight control method | |
| CN106081098A (en) | A kind of unmanned plane | |
| CN108357667B (en) | Buffer-type undercarriage for rotary wind type unmanned plane | |
| CN215622661U (en) | Undercarriage and fixed wing unmanned aerial vehicle | |
| RU2748623C1 (en) | Small-sized unmanned aircraft system | |
| CN212829062U (en) | VTOL aerial survey unmanned aerial vehicle | |
| CN106915464A (en) | The landing-gear and mode of a kind of aircraft | |
| CN208439425U (en) | A kind of novel combined fixed-wing unmanned plane | |
| CN206031776U (en) | Unmanned aerial vehicle | |
| RU2104903C1 (en) | Helicopter-aerostat complex | |
| CN208963331U (en) | Unmanned plane lifting gear, unmanned plane and automobile | |
| CN210310861U (en) | Automatic expansion undercarriage | |
| CN114408201A (en) | Fixed-wing unmanned aerial vehicle recovery system and method | |
| CN207809755U (en) | Stratospheric airship aerodynamic arrangement structure with auxiliary stabilization | |
| CN206231611U (en) | Off-loadable unmanned aerial vehicle body structure |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |